JP2002021503A - Draft system of a pair of platforms of blades arranged in parallel - Google Patents

Draft system of a pair of platforms of blades arranged in parallel

Info

Publication number
JP2002021503A
JP2002021503A JP2001180380A JP2001180380A JP2002021503A JP 2002021503 A JP2002021503 A JP 2002021503A JP 2001180380 A JP2001180380 A JP 2001180380A JP 2001180380 A JP2001180380 A JP 2001180380A JP 2002021503 A JP2002021503 A JP 2002021503A
Authority
JP
Japan
Prior art keywords
platforms
platform
gas
pair
liner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
JP2001180380A
Other languages
Japanese (ja)
Other versions
JP4047560B2 (en
Inventor
Serge Antunes
セルジユ・アンテユーヌ
Eric Bil
エリツク・ビル
Isabelle Bourriaud
イザベル・ブリヨー
Jude Maurice
モーリス・ジユデ
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of JP2002021503A publication Critical patent/JP2002021503A/en
Application granted granted Critical
Publication of JP4047560B2 publication Critical patent/JP4047560B2/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

PROBLEM TO BE SOLVED: To provide a draft system of a pair of platforms of blades arranged in parallel capable of effectively increasing heat exchange of draft gas while damping the vibration of the platforms of the blades sufficiently without impairing airtightness. SOLUTION: Airtight liners 9 made of metallic thin plates are put below a pair of platforms of the blades 6 to cover a clearance 7. The airtight liner 9 sends draft gas in the platforms 6 from a circulation path 10 and makes it to flow continuously. For this reason, exhaust ports 11, 12 are provided. Moreover, the liner 9 is provided with a protruding part 13 to increase heat exchange due to the impact of gas sent hard below the platforms 6.

Description

【発明の詳細な説明】DETAILED DESCRIPTION OF THE INVENTION

【０００１】[0001]

【発明の属する技術分野】本発明は、並置された羽根の
プラットフォーム対の通風システム（ｓｙｓｔｅｍｅ
ｄｅ ｖｅｎｔｉｌａｔｉｏｎ）に関する。FIELD OF THE INVENTION The present invention relates to a system of ventilation of a pair of side-by-side blade platforms.
de ventilation).

【０００２】[0002]

【従来の技術】一般に、タービン（エンジン）にある通
風システムは、ガス流を、このガスとは異なる温度にな
る構造部分に送風して、前記構造部分が過熱しすぎない
ように保護し、あるいは幾つかの用途では、熱膨張を調
整するとともに、装置の流出効率（ｒｅｎｄｅｍｅｎｔ
ｄ‘ｅｃｏｕｌｅｍｅｎｔ）を改善する遊びの調整を
行う。本発明は、同一周囲に並んで設置された羽根のプ
ラットフォームの通風に関する。羽根のプラットフォー
ムは、羽根の下部を隔てる空洞を覆い、装置の流管の輪
郭を、いっそう均整のとれたものにする。空洞は、通風
ガスを吹き込むことによって有効に利用される。しかし
ながら、通風ガスは、プラットフォームが並置される隙
間から空洞を出てしまい、その場合には殆ど効果がなく
なる。そのため、プラットフォームの下に気密手段を配
置して、並置した隙間を塞ぐ。気密部品は、通風を望む
プラットフォーム部分に通風ガスが到達するように構成
される。プラットフォーム部分は、排気口を備え、ガス
は、空洞を出る際に排気口を通過する。ガスは、特に、
これらの排気口を通ることによって所望の熱交換を発生
する。2. Description of the Related Art Generally, a ventilation system in a turbine (engine) blows a gas stream to a structural part having a temperature different from that of the gas to protect the structural part from being overheated, or In some applications, thermal expansion may be adjusted and the outflow efficiency of the device may be adjusted.
adjustment of play to improve d'ecoulment). The invention relates to the ventilation of vane platforms arranged side by side on the same circumference. The blade platform covers the cavity separating the lower portions of the blades, making the device flow tubes more evenly contoured. The cavity is effectively used by blowing ventilation gas. However, the ventilation gas leaves the cavity through the gap where the platforms are juxtaposed, in which case it has little effect. Therefore, an airtight means is arranged under the platform to close the juxtaposed gap. The hermetic component is configured such that the ventilated gas reaches the platform portion where ventilation is desired. The platform portion is provided with an outlet, and gas passes through the outlet as it exits the cavity. Gas, in particular,
The desired heat exchange is generated by passing through these exhaust ports.

【０００３】本発明は、フランス特許第２７５８８５５
号に記載されたシステムを改良するものである。この特
許では、気密部品が、プラットフォームの下面に置かれ
た薄板からなる金属ライナであり、装置の作動中に可動
羽根に生じる遠心力によってプラットフォームが押され
る。薄板は、孔を備えており、この孔を通って通風ガス
がプラットフォームに到達する。これらの孔は、プラッ
トフォームにあけられた収集溝に通じており、収集溝
は、蛇状端部、すなわち、同じくプラットフォームにあ
けられる蛇管を構成し、通風ガスは、プラットフォーム
を貫通する排気口に達するために、ここを通らなければ
ならない。熱交換は、対流によって行われる。だが、こ
うした構成はあまり有効ではないことが判明した。[0003] The present invention relates to French Patent No. 2,758,855.
This is an improvement on the system described in the above item. In this patent, the hermetic component is a metal liner consisting of a thin plate placed on the underside of the platform, during which the centrifugal forces on the movable blades push the platform. The sheet is provided with holes through which the ventilation gas reaches the platform. These holes lead to a collecting groove drilled in the platform, which forms a serpentine end, i.e., a serpentine tube also drilled in the platform, and the ventilated gas reaches the exhaust through the platform. In order to do so, you have to pass here. Heat exchange takes place by convection. However, such a configuration proved to be less effective.

【０００４】[0004]

【発明が解決しようとする課題】従って、本発明の目的
は、薄板（ｔｏｌｅ）または金属板製の気密ライナを改
良して、気密性を損なわずに、羽根のプラットフォーム
の振動を十分に減衰しながら、通風ガスの熱交換を有効
に増大することにある。SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide an improved hermetic liner made of a sheet or metal plate to sufficiently dampen the vibration of the blade platform without compromising hermeticity. However, the purpose is to effectively increase the heat exchange of the ventilation gas.

【０００５】[0005]

【課題を解決するための手段】本発明によれば、ライナ
は、孔の場所に突出部（ｂｏｓｓａｇｅｓ）を備え、チ
ャンバが、プラットフォームと突出部との間に形成さ
れ、排気口が、チャンバに連通している。その結果、ラ
イナの孔を通る通風ガスは、一定の速度でプラットフォ
ームの方に送風される。この速度は、プラットフォーム
に対する衝撃を形成することにより熱交換を増大する。According to the present invention, a liner is provided with protrusions at the location of the holes, a chamber is formed between the platform and the protrusion, and an exhaust port is formed in the chamber. Communicating. As a result, the ventilation gas passing through the hole in the liner is blown toward the platform at a constant speed. This speed increases heat exchange by creating an impact on the platform.

【０００６】有利には、突出部が、複数の孔または複数
の排気口の各々を含むように、プラットフォームの接合
部に平行に延びている。さらに有利には、排気口が、そ
れぞれ孔に向かい合って、通風ガスの流れを容易にして
いる。Advantageously, the projection extends parallel to the junction of the platform so as to include each of a plurality of holes or a plurality of vents. Further advantageously, the exhaust ports are respectively opposite the holes to facilitate the flow of the ventilation gas.

【０００７】次に、本発明の可能な実施例を添付図を参
照しながら説明する。Next, a possible embodiment of the present invention will be described with reference to the accompanying drawings.

【０００８】[0008]

【発明の実施の形態】本発明で検討される羽根は、ター
ビンの可動羽根であり、特に高圧タービンの第一段の可
動羽根である。この羽根は、隣接する燃焼室により非常
に高い加熱を被り、ディスク１の溝に挿入されている。
羽根は、ディスク１の溝に係合する根元部２と、支持脚
３と、燃焼ガスの流路あるいは流管５に配置されて羽根
の有効部分を構成する羽根部４とを含む。さらに、支持
脚３と羽根部４との接合部の周囲に延びている、ほぼ円
弧形のプラットフォーム６を含む。隣接する羽根対のプ
ラットフォーム６は、相互の間に隙間７だけを残して並
置される。隙間７は、空洞８に流管５を結合する。空洞
８は、隣接する羽根のプラットフォーム６および支持脚
３と、ディスク１とによって画定される。隙間７は、こ
こでは、空洞８に配置された金属薄板のライナ９からな
る気密部品により閉じられる。このライナは、プラット
フォーム６の下面と、支持脚３の間の隙間７とを覆う。DETAILED DESCRIPTION OF THE INVENTION The blade considered in the present invention is a movable blade of a turbine, in particular a first stage movable blade of a high pressure turbine. The blades are subjected to very high heating by the adjacent combustion chamber and are inserted into the grooves of the disc 1.
The blade includes a root portion 2 that engages with the groove of the disk 1, a support leg 3, and a blade portion 4 that is disposed in a combustion gas flow path or flow tube 5 and that constitutes an effective portion of the blade. It further includes a substantially arcuate platform 6 extending around the junction of the support leg 3 and the wing 4. The platforms 6 of adjacent blade pairs are juxtaposed, leaving only a gap 7 between each other. The gap 7 connects the flow tube 5 to the cavity 8. The cavity 8 is defined by the adjacent blade platform 6 and the support leg 3 and the disk 1. The gap 7 is here closed by a hermetic component consisting of a sheet metal liner 9 arranged in a cavity 8. This liner covers the lower surface of the platform 6 and the gap 7 between the support legs 3.

【０００９】冷たい通風ガスは、隣接する羽根の一方の
根元部２および支持脚３を通ってあけられた管路１０に
よって、あるいは空洞８の上流にある羽根間の孔によっ
て、空洞８に吹き込まれる。ガスは、一般に、コンプレ
ッサまたはタービンから送られる。しかし、管路１０を
構成する可能性は数多くあり、他の様々な文献に記載さ
れているので、ここでは詳述しない。排気口１１は、冷
却が必要な場所でプラットフォーム６を貫通し、ガスが
空洞８を抜けて流管５に入るようにする。ライナ９は、
排気口１１の正面にそれぞれ配置される孔１２を備え
る。さらに、これらの孔１２の場所でライナ９に突出部
１３を形成し、突出部とプラットフォーム６との間にチ
ャンバ１４を形成する。図２では、突出部１３が、隙間
７に長手方向に延長されて複数の排気孔１１および孔１
２を含んでいることが分かる。[0009] Cold ventilation gas is blown into cavity 8 by a conduit 10 drilled through one root 2 and support leg 3 of an adjacent blade, or by a hole between the blades upstream of cavity 8. . The gas is generally sent from a compressor or a turbine. However, there are many possibilities for configuring the conduit 10 and these are described in various other documents and will not be described in detail here. The exhaust port 11 penetrates the platform 6 where cooling is required and allows gas to pass through the cavity 8 and into the flow tube 5. Liner 9
A hole 12 is provided at the front of the exhaust port 11. Furthermore, a projection 13 is formed in the liner 9 at the location of these holes 12, and a chamber 14 is formed between the projection and the platform 6. In FIG. 2, the protrusion 13 extends in the gap 7 in the longitudinal direction, and the plurality of exhaust holes 11 and the holes 1 are formed.
2 is included.

【００１０】突出部の目的は、孔１２を通ってプラット
フォーム６の方に送られる通風ガスが、衝撃によって、
対流により冷却を行っていた従来技術の構成よりも強
く、突出部を冷却することにある。[0010] The purpose of the projections is to allow the ventilation gas delivered through the holes 12 to
The purpose of the present invention is to cool the protruding portion more strongly than the prior art configuration in which cooling is performed by convection.

【００１１】ライナ９は、湾曲端がある場合を除いて、
突出部１２以外でプラットフォーム６の下面とほぼ係合
する。ライナ９は、ディスク１の回転によって生じる遠
心力が及ぼされるとき、一定の圧力でプラットフォーム
６の下に置かれるように十分に柔軟性があり、プラット
フォームの振動を減衰する役割をする。[0011] The liner 9 has a
Except for the protruding portion 12, it substantially engages with the lower surface of the platform 6. The liner 9 is flexible enough to be placed under the platform 6 at a constant pressure when subjected to the centrifugal force created by the rotation of the disk 1 and serves to damp the vibration of the platform.

【図面の簡単な説明】[Brief description of the drawings]

【図１】羽根対の正面図である。FIG. 1 is a front view of a blade pair.

【図２】システムの斜視図である。FIG. 2 is a perspective view of the system.

【符号の説明】[Explanation of symbols]

１ ディスク ２ 根元部 ３ 支持脚 ４ 羽根部 ６ プラットフォーム対 ７ 接合部 ８ 空洞 ９ 気密ライナ １０ ガスの吹き込み手段 １１ 排気口 １２ 孔 １３ 突出部 １４ チャンバ DESCRIPTION OF SYMBOLS 1 Disc 2 Root part 3 Support leg 4 Blade part 6 Platform pair 7 Joint part 8 Cavity 9 Airtight liner 10 Gas blowing means 11 Exhaust port 12 Hole 13 Projection part 14 Chamber

───────────────────────────────────────────────────── フロントページの続き (72)発明者 イザベル・ブリヨー フランス国、77190・ダマリー・レ・リ、 リユ・マルク・シヤガール・945 (72)発明者 モーリス・ジユデ フランス国、77190・ダマリー・レ・リ、 リユ・ジヤン・モネ・144 Ｆターム(参考） 3G002 AA04 AA06 AB01 BA02 BB03 FA04 FA06 FB02 FB04 HA01 ──────────────────────────────────────────────────の Continuing on the front page (72) Inventor Isabel Briyo, France, 77190 Damarie-les-Lis, Rille-Marc-Shigaard-945 Li, Liu Jiang Monet 144 F term (reference) 3G002 AA04 AA06 AB01 BA02 BB03 FA04 FA06 FB02 FB04 HA01

Claims (3)

【特許請求の範囲】[Claims] 【請求項１】 空洞（８）を覆う並置された羽根のプラ
ットフォーム対（６）の通風システムであって、空洞内
に通風ガスを吹き込む手段（１０）と、空洞内のプラッ
トフォームの下に配置されて孔（１２）を備える気密ラ
イナ（９）と、プラットフォームを貫通する排気口（１
１）とを含み、ライナが、孔（１２）の場所に突出部
（１３）を備え、チャンバ（１４）が、プラットフォー
ムと突出部との間に形成され、排気口が、チャンバに連
通していることを特徴とするシステム。1. A ventilation system for juxtaposed vane platform pairs (6) covering a cavity (8), comprising means (10) for blowing ventilation gas into the cavity, and arranged below the platform in the cavity. Airtight liner (9) with vent holes (12) and exhaust ports (1
1) wherein the liner comprises a projection (13) at the location of the hole (12), a chamber (14) is formed between the platform and the projection, and an exhaust port communicates with the chamber. System. 【請求項２】 突出部が、プラットフォームの接合部
（７）に平行に延びていることを特徴とする請求項１に
記載の並置された羽根のプラットフォーム対の通風シス
テム。2. Ventilation system according to claim 1, characterized in that the projections extend parallel to the joints (7) of the platforms. 【請求項３】 排気口（１１）が、それぞれ孔（１２）
と向かい合っていることを特徴とする請求項１または２
に記載の並置された羽根のプラットフォーム対の通風シ
ステム。3. An exhaust port (11) having a hole (12).
3. The method according to claim 1, wherein
The ventilation system of a side-by-side blade platform pair of claim 5.
JP2001180380A 2000-06-15 2001-06-14 Side-by-side blade platform pair ventilation system Expired - Lifetime JP4047560B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0007611A FR2810365B1 (en) 2000-06-15 2000-06-15 SYSTEM FOR VENTILATION OF A PAIR OF JUXTAPOSED DAWN PLATFORMS
FR0007611 2000-06-15
US09/883,948 US6457935B1 (en) 2000-06-15 2001-06-20 System for ventilating a pair of juxtaposed vane platforms

Publications (2)

Publication Number Publication Date
JP2002021503A true JP2002021503A (en) 2002-01-23
JP4047560B2 JP4047560B2 (en) 2008-02-13

Family

ID=26212467

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2001180380A Expired - Lifetime JP4047560B2 (en) 2000-06-15 2001-06-14 Side-by-side blade platform pair ventilation system

Country Status (4)

Country Link
US (1) US6457935B1 (en)
EP (1) EP1164253B1 (en)
JP (1) JP4047560B2 (en)
FR (1) FR2810365B1 (en)

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US6457935B1 (en) 2002-10-01
FR2810365A1 (en) 2001-12-21

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